EP0201374B1 - Système d'actionnement hydraulique d'un organe dans une fusée - Google Patents

Système d'actionnement hydraulique d'un organe dans une fusée Download PDF

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Publication number
EP0201374B1
EP0201374B1 EP86400689A EP86400689A EP0201374B1 EP 0201374 B1 EP0201374 B1 EP 0201374B1 EP 86400689 A EP86400689 A EP 86400689A EP 86400689 A EP86400689 A EP 86400689A EP 0201374 B1 EP0201374 B1 EP 0201374B1
Authority
EP
European Patent Office
Prior art keywords
hydraulic fluid
pipe
interface
tank
rocket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP86400689A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0201374A1 (fr
Inventor
François Paris
Claude Johnson
Albert Lecrivain
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Centre National dEtudes Spatiales CNES
Original Assignee
Centre National dEtudes Spatiales CNES
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Centre National dEtudes Spatiales CNES filed Critical Centre National dEtudes Spatiales CNES
Publication of EP0201374A1 publication Critical patent/EP0201374A1/fr
Application granted granted Critical
Publication of EP0201374B1 publication Critical patent/EP0201374B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/805—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles

Definitions

  • the present invention relates to a hydraulic system for actuating an organ in an assembly whose operation is autonomous at least for a limited period, for example a vehicle or an aircraft and among these in particular a rocket.
  • the invention therefore relates to the mechanical industries and vehicles.
  • the energy required for these jacks is usually supplied by a high pressure hydraulic pump which is driven by a gas or electric motor, all of which forms a group embedded in the rocket.
  • Document FR-A 2 068 765 thus describes a nozzle for a jet engine equipped with hydraulic means capable of tilting it.
  • a source of hydraulic fluid comprising an on-board reservoir, a means for pressurizing the fluid, and a pipe bringing this pressurized fluid to the member to be controlled.
  • the energy required to control the various bodies to be tested is delivered by non-on-board energy sources, gas under pressure or electric current to drive the on-board group while avoiding using the sources of on-board energy, both so as not to increase the on-board mass and because these on-board sources may not yet be available.
  • the object of the present invention is to remedy this drawback by proposing a system of high reliability, of low mass and of reduced maintenance.
  • the system represented in FIG. 1 comprises means 100 on board the rocket, means 200 located on the ground and an onboard-self interface 300.
  • the means 100 on board include a bottle of pressurized helium 110 (on the right side in the figure), a fluid reservoir 130 (on the left) and a control electronics 150 (in the center).
  • the pressure of the reservoir 110 is for example 60 MPa and that of the reservoir 130 of 30 MPa.
  • the helium contained in the bottle 110 is directed into the tank 130 by a conduit 111 provided with a filter 112. There are then two parallel conduits 113 and 114 each provided with pressure regulating solenoid valve 115 and 116. The first is also associated with a regulator 117.
  • the bottle 110 is also equipped with a pressure sensor 118.
  • the fluid reservoir 130 receives, at its upper part, the helium under pressure via an inlet duct 131, it comprises a diaphragm-float 132, separating the helium from the hydraulic fluid to prevent its dissolution. It is equipped with a liquid level sensor 133 and a pressure sensor 134.
  • the assembly constituted by the solenoid valves 115, 116, the pressure sensors 118, 134 is connected to the control electronics 150, which performs various comparisons between the measured quantities and reference values and consequently issues orders of valve opening or closing control.
  • an introduction conduit on the bottle side 110 helium 119 in the bottle this conduit being provided with a filter 121 connected to an inflation solenoid valve 122 and to an inlet conduit 123.
  • a conduit for introducing fluid 136 into the tank this duct being connected to a filter 137, a solenoid valve 138, a filter 139 and a hydraulic fluid inlet duct 140.
  • the reservoir 130 also comprises, at its lower part, a discharge duct 141 provided with a filter 142 and an implementation solenoid valve 143. This last valve is connected to the member to be controlled 168, shown diagrammatically in this figure 1.
  • the edge-to-ground interface 300 includes a junction for introducing hydraulic fluid 310 (self-sealing valves or sleeves of known type), which allow the hydraulic fluid inlet conduit 140 to be connected to a source of hydraulic fluid 230 located on the ground.
  • the interface also comprises a helium inlet junction 320 connecting the conduit 123 to a source of helium 210 under high pressure.
  • the interface 300 also includes various conventional electrical connections making it possible to connect the control member 150 and the inflation and filling valves 122 and filling 138 to a control circuit 250 located on the ground.
  • the hydraulic fluid for example oil
  • the solenoid valve 138 When one wishes to control a member of the rocket, while the rocket is still on the ground, the hydraulic fluid (for example oil) is introduced into the reservoir 130 by opening the solenoid valve 138.
  • the pressurized fluid is transmitted to the member to be controlled by the implementation valve 143, its pressure being able to come either from the source 230 or from the bottle 110 by means of compressed helium.
  • the fluid is evacuated to the open air and without pressure through the conduit 171 coming from the member 168.
  • the interface 300 In flight, the interface 300 is separated (on takeoff all the connections are torn off and the connections are interrupted).
  • the control of the member is always carried out by the same hydraulic fluid but, this time, thanks to the helium pressure introduced into the fluid reservoir 130.
  • the control fluid is transmitted to the member through the same valve 143 which was used for the ground tests.
  • FIG. 2 illustrates a simpler embodiment in which the rocket motors are supposed to be powered by liquid hydrogen.
  • the rocket comprises, on board, a pump 160 connected, on the one hand, to a reservoir of liquid hydrogen not shown and, d on the other hand, to a hydrogen delivery pipe 161, which is connected to a rocket engine (not shown).
  • the system comprises a bypass 162 which is pricked on the conduit 161 and is provided with means 163 for heating the bypass fluid and vaporizing it.
  • the duct 162 comprises a non-return valve 164 and opens into a fluid reservoir 165 (of the type of the reservoir 130 illustrated in FIG. 1).
  • valve 166 with electric or pneumatic control.
  • the latter is connected, via a conduit 167, to the member to be controlled 168 which is, in the example illustrated, constituted by a servovalve connected to a jack.
  • the servovalve is connected to an evacuation duct 169 provided with a non-return valve 170 and an evacuation 171 out of the rocket.
  • the system also comprises, in the edge-to-ground interface 300, a junction 310 connected to a source of pressurized fluid 230 located on the ground.
  • the junction 310 communicates with a conduit 172 provided with a filter 173 connected to the conduit 167 downstream of the valve 166.
  • the hydraulic fluid is introduced by the junction 310 to the member 168 by the conduits 172 and 167, the valve 166 being closed.
  • This fluid is identical to the fluid used in flight, delivered by the pressure exchanger tank 165.
  • the hydraulic fluid is discharged after use through the conduit 171. On the ground the effluent is returned to the source 230, which is a conventional hydraulic power station.
  • FIG. 3 corresponds to a rocket equipped with a water pump 175 supplied by a reservoir 174 and pumping the water under high pressure into a conduit 176, for example for cooling combustion gases which actuate a turbine driving the pump 175 between other.
  • a bypass 177 of the conduit 176 provided with a non-return valve 178, is connected to the conduit 179 for introducing the pressurized working fluid into the member 168 which is also of the servovalve and jack type.
  • the on-board means may further comprise a small water accumulator 180, under gas pressure introduced by the valve 186, which can temporarily actuate the member before starting the pump, and which, being placed in position high, can be used as a degasser.
  • the starting of the pump 175 can be accompanied by a certain entrainment of bubbles.
  • the water at low pressure is evacuated the atmosphere by the valve 181 and the conduit 182, through a non-return valve 187 supported by a weak spring 183 to avoid draining of the member 168 by a free flow.
  • the means allowing the ground tests comprise a non-return junction 310 connected to a source 230 of pressurized fluid supplying the member 168 by a conduit 184, a filter 185 and the conduit 179.
  • conduit 182 On the ground, the fluid evacuated through conduit 182 is ra led to the source 230 by the separable interface 330.
  • this assembly may not carry any instrument, valve or filter other than those shown, the filling valves, manometers and flow meters being part of the source 230.
  • This valve 231 also allows the oil to be drained in the event of tests without autonomous operation of the assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Remote Sensing (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP86400689A 1985-04-04 1986-03-28 Système d'actionnement hydraulique d'un organe dans une fusée Expired - Lifetime EP0201374B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8505144A FR2580038B1 (enrdf_load_stackoverflow) 1985-04-04 1985-04-04
FR8505144 1985-04-04

Publications (2)

Publication Number Publication Date
EP0201374A1 EP0201374A1 (fr) 1986-11-12
EP0201374B1 true EP0201374B1 (fr) 1990-03-14

Family

ID=9317950

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86400689A Expired - Lifetime EP0201374B1 (fr) 1985-04-04 1986-03-28 Système d'actionnement hydraulique d'un organe dans une fusée

Country Status (4)

Country Link
US (1) US4757960A (enrdf_load_stackoverflow)
EP (1) EP0201374B1 (enrdf_load_stackoverflow)
DE (1) DE3669564D1 (enrdf_load_stackoverflow)
FR (1) FR2580038B1 (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107867411A (zh) * 2017-09-20 2018-04-03 上海空间推进研究所 一种全自动在轨补加装置

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6070408A (en) * 1997-11-25 2000-06-06 Caterpillar Inc. Hydraulic apparatus with improved accumulator for reduced pressure pulsation and method of operating the same
US6802406B2 (en) * 2002-12-17 2004-10-12 United Defense, L.P. Recoil brake isolation system
US7687930B2 (en) * 2007-09-10 2010-03-30 Hansen Jr Howard Otto Solar/geothermal powered thermodynamic hydro electric generating system
US7579700B1 (en) * 2008-05-28 2009-08-25 Moshe Meller System and method for converting electrical energy into pressurized air and converting pressurized air into electricity
CN108045604B (zh) * 2017-12-07 2020-11-24 上海宇航系统工程研究所 一种连接器气动随动装置

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2170890A (en) * 1937-04-08 1939-08-29 Link Belt Co Removable accumulator
US2278181A (en) * 1939-05-17 1942-03-31 Sulzer Ag Engine and gear coupling
US2290479A (en) * 1939-06-02 1942-07-21 Mercier Jean Hydraulic control system
US2866385A (en) * 1956-01-10 1958-12-30 Northrop Aircraft Inc Automatic jet engine starting device
US3049877A (en) * 1956-02-13 1962-08-21 Thiokol Chemical Corp Nozzle for reaction motor
US3908933A (en) * 1956-06-26 1975-09-30 Us Navy Guided missile
FR1237219A (fr) * 1959-06-16 1960-07-29 France Etat Tuyère orientable
US3163985A (en) * 1962-07-31 1965-01-05 John V Bouyoucos Hydraulic energy storage system
FR1469194A (fr) * 1965-12-30 1967-02-10 Onera (Off Nat Aerospatiale) Perfectionnements apportés aux missiles à générateur de gaz à au moins un ergolliquide soumis à la pression directe d'un gaz de chasse et aux installations de lancement de tels missiles
GB1250491A (enrdf_load_stackoverflow) * 1967-12-15 1971-10-20
US3692258A (en) * 1968-10-03 1972-09-19 Arthur R Parilla Missile configurations,controls and utilization techniques
GB1291586A (en) * 1969-10-23 1972-10-04 Rolls Royce Propulsive jet nozzle assembly
US3911678A (en) * 1974-11-07 1975-10-14 Shafer Valve Co Safety shut-off for pump
FR2444805A1 (fr) * 1978-12-20 1980-07-18 Europ Propulsion Dispositif de deviation du jet d'une tuyere de propulseur-fusee

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107867411A (zh) * 2017-09-20 2018-04-03 上海空间推进研究所 一种全自动在轨补加装置
CN107867411B (zh) * 2017-09-20 2021-02-09 上海空间推进研究所 一种全自动在轨补加装置

Also Published As

Publication number Publication date
US4757960A (en) 1988-07-19
FR2580038A1 (enrdf_load_stackoverflow) 1986-10-10
DE3669564D1 (de) 1990-04-19
FR2580038B1 (enrdf_load_stackoverflow) 1987-06-19
EP0201374A1 (fr) 1986-11-12

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